EASA AD No : 2010-0157 

EASA Form 110 Page 1/2 

EASA AIRWORTHINESS DIRECTIVE 

AD No.: 2010-0157 

Date: 03 August 2010 

Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with 

Regulation (EC) No 216/2008 on behalf of the European Community, its Member States and 

of the European third countries that participate in the activities of EASA under Article 66 of 

that Regulation. 

This AD is issued in accordance with EC 1702/2003, Part 21A.3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the 

continuing airworthiness of an aircraft shall be ensured by accomplishing any applicable ADs. Consequently, no person may operate 

an aircraft to which an AD applies, except in accordance with the requirements of that AD, unless otherwise specified by the Agency 

[EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption]. 

Type Approval Holder’s Name : 

Fokker Services B.V.

Type/Model designation(s) : 

F27 Mark 050, 0502 and 0604 aeroplanes 

TCDS Number : EASA.A.036 

Foreign AD : Not applicable 

Supersedure : None 

ATA 28 Fuel – Fuel Quantity Probe & Wiring Installation – Inspection / 

Modification [Fuel Tank Safety] 

Manufacturer(s): Fokker Aircraft B.V. 

Applicability: F27 Mark 050, 0502 and 0604 aeroplanes, all serial numbers. 

Reason: Prompted by an accident of a Boeing 747-131 (flight TWA800), the Federal 

Aviation Administration (FAA) has published Special Federal Aviation 

Regulation (SFAR) 88, and the Joint Aviation Authorities (JAA) has 

published Interim Policy INT/POL/25/12. The design review conducted by 

Fokker Services on the Fokker 50 and Fokker 60 in response to these 

regulations revealed that, if chafing occurs between the Fuel Quantity Probe 

(FQP) and the probe wiring, with additional factors, this may result in an 

ignition source in the wing tank vapour space. 

This condition, if not corrected, in combination with flammable fuel vapours, 

could result in a wing fuel tank explosion and consequent loss of the 

aeroplane. 

For the reasons described above, this AD requires a one-time inspection to 

check for the presence of a rubber sleeve and cable tie near each FQP in 

both wing tanks and, depending on findings, the installation of a sleeve and 

cable tie. 

Effective Date: 17 August 2010 
EASA AD No : 2010-0157 

EASA Form 110 Page 2/2 

Required Action(s) 

and Compliance 

Time(s): 

Required as indicated, unless accomplished previously. 

(1) At a scheduled opening of the fuel tanks, but not later than 13 years 

after the effective date of this AD, inspect for the presence of the rubber 

sleeve and cable tie on the cables of each FQP in accordance with Part 

1 of the Accomplishment Instructions of Fokker Services Service Bulletin 

(SB) SBF50-28-027. 

(2) If, during the inspection as required by paragraph (1) of this AD, an FQP 

does not have the sleeve and/or cable tie installed, before next flight, 

install the rubber sleeve and cable tie on the affected FQP and wiring, in 

accordance with Part 2 of the Accomplishment Instructions of Fokker 

Services SBF50-28-027. 

(3) From the effective date of this AD, do not install a FQP or FQP wiring on 

any aeroplane, unless the rubber sleeve and cable tie are installed in 

compliance with the requirements of this AD. 

(4) Compliance with the requirements of paragraph (3) of this AD can be 

demonstrated by: 

(4.1) Revising as follows the approved aircraft maintenance programme 

for which the Operator or the Owner ensures the continuing 

airworthiness of each operated aeroplane: 

incorporate the CDCCL item in accordance with the information in 

paragraph 1.L.(1)(c) of Fokker Services SB SBF50-28-027, 

 and 

(4.2) Complying with the approved aircraft maintenance programme 

described in paragraph (4.1) of this AD. 

Ref. Publications: 

Fokker Services SBF50-28-027 dated 27 May 2010. 

The use of later approved revisions of this document is acceptable for 

compliance with the requirements of this AD. 

Remarks: 1. If requested and appropriately substantiated, EASA can approve 

Alternative Methods of Compliance for this AD. 

2. This AD was posted on 29 June 2010 as PAD 10-066 for consultation 

until 27 July 2010. No comments were received during the consultation 

period. 

3. Enquiries regarding this AD should be referred to the Airworthiness 

Directives, Safety Management & Research Section, Certification 

Directorate, EASA. E-mail ADs@easa.europa.eu. 

4. For any question concerning the technical aspects of the requirements in 

this AD, please contact: 

Fokker Services B.V., Technical Services Dept., P.O.Box 231, 

2150 AE Nieuw-Vennep, The Netherlands; 

telephone (31) 252-627-350; facsimile (31) 252-627-211; 

e-mail: technicalservices.fokkerservices@fokker.com 

The referenced publication can be downloaded from 

www.myfokkerfleet.com